2024-12-06: Fuselage

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2024-12-06 De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.): Amendment 39-22770; Docket No. FAA-2023-1885; Project Identifier MCAI-2022-01484-T. (a) Effective Date This airworthiness directive (AD) is effective August 21, 2024. (b) Affected ADs None. (c) Applicability This AD applies to De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC-8-401 and -402 airplanes, certificated in any category, having serial numbers 4001 and 4003 through 4624 inclusive. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of moisture in the wing-to-fuselage joint, between the mating front spar and rear spar frame segments. The FAA is issuing this AD to address potential corrosion and structural degradation of the wing-to-fuselage joint. The unsafe condition, if not addressed, could result in wing separation from the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Action At the applicable compliance times specified in paragraph (g)(1) or (2) of this AD, in accordance with Section 3.B., of the Accomplishment Instructions of De Havilland Aircraft of Canada Service Bulletin 84-53-81, Revision A, dated August 23, 2022, complete a general visual inspection of the fuselage spar frames and around the frame bolts for signs of moisture ingress ( i.e., stains and streaks), accomplish other specified actions, and if necessary, perform an ultrasonic test. Do all applicable ultrasonic tests before further flight. If, during any ultrasonic test, any corrosion or structural degradation is found, before further flight, repair using a method approved by the Manager, International Validation Branch, FAA; or Transport Canada; or De Havilland Aircraft of Canada Limited's Transport Canada Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (1) For airplanes that, as of the effective date of this AD, have accumulated less than 32,000 total flight cycles: before accumulating 40,000 total flight cycles. (2) For airplanes that, as of the effective date of this AD, have accumulated 32,000 or more total flight cycles: within 8,000 flight hours or 48 months, whichever occurs first after the effective date of this AD. (h) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using De Havilland Aircraft of Canada Limited Service Bulletin 84-53-81, dated May 27, 2022. (i) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the manager, International Validation Branch, mail it to the address identified in paragraph (j) of this AD or email to 9-AVS-AIR-730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Validation Branch, FAA; or Transport Canada; or De Havilland Aircraft of Canada Limited's Transport Canada DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (j) Additional Information For more information about this AD, contact Deep Gaurav, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; email deep.gaurav@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) De Havilland Aircraft of Canada Limited Service Bulletin 84-53-81, Revision A, dated August 23, 2022. (ii) [Reserved] (3) For De Havilland Aircraft material incorporated by reference in this AD, contact De Havilland Aircraft of Canada Limited, Dash 8 Series Customer Response Centre, 5800 Explorer Drive, Mississauga, Ontario, L4W 5K9, Canada; telephone 855-310-1013 or 647-277-5820; email thd@dehavilland.com; website dehavilland.com. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locationsoremailfr.inspection@nara.gov. Issued on July 10, 2024. James D. Foltz, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024-15657 Filed 7-16-24; 8:45 am]BILLING CODE 4910-13-P